| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 用于消雹降雨的遥控飞机及消雹降雨方法 | CN201710546418.6 | 2017-07-06 | CN107318546A | 2017-11-07 | 李晓东; 李文铎 |
| 本发明公开了一种用于消雹降雨的遥控飞机及消雹降雨方法，采用遥控飞机将碘化银撒播于云层中，安全性较好，空域管制相对较宽松，适应性强；将碘化银溶解于丙酮-酒精溶液，避免了氯酸铵的使用，减少污染，有更好的环保性；而且本发明中避免了使用爆炸品，更加安全，而且库存管理、运输管理、操作管理的管制宽松；机翼可折叠，便于存储、运输、操作，降低成本；含碘化银的丙酮-酒精溶液在喷气式发动机尾部喷管处燃烧，避免了对喷气式发动机的腐蚀，延长使用寿命。 | ||||||
| 2 | 具有铰接尾桁短距起落/垂直起落自由翼飞机及其推动方法 | CN94191348.1 | 1994-01-21 | CN1051974C | 2000-05-03 | 埃尔伯特·拉特安; 休·J·施米特科 |
| 一种VTOL/STOL自由翼飞机(100)包括一自由翼(110)，其翼翅对置于机身(102)的两侧，并分别与彼此临近的固定连接于机身的固定翼或中心根部(117)相连接，可绕一翼展轴线(112)自由转动。可转动地连接于机身(102)的一尾桁组件(120)的尾部远端设有水平和竖直尾翼表面(138、140)。由驾驶员或遥控器操作者控制齿轮机构(150)或螺杆机构(160)，从而可选择性地使机身和尾桁组件相对枢转，使机身倾斜或朝向上而实现VTOL/STOL飞行。 | ||||||
| 3 | 具有铰接尾桁短距起落/垂直起落自由翼飞机 | CN94191348.1 | 1994-01-21 | CN1118591A | 1996-03-13 | 埃尔伯特·拉特安; 休·J·施米特科 |
| 一种VTOL/STOL自由翼飞机(100)包括一自由翼(110)，其翼翅对置于机身(102)的两侧，并分别与彼此临近的固定连接于机身的固定翼或中心根部(117)相连接，可绕一翼展轴线(112)自由转动。可转动地连接于机身(102)的一尾桁组件(120)的尾部远端设有水平和竖直尾翼表面(138、140)。由驾驶员或遥控器操作者控制齿轮机构(150)或螺杆机构(160)，从而可选择性地使机身和尾桁组件相对枢转，使机身倾斜或朝向上而实现VTOL/STOL飞行。 | ||||||
| 4 | Articulated tail struts with stol / vtol freely wing aircraft | JP51715094 | 1994-01-21 | JPH08508954A | 1996-09-24 | シュミットル・ヒュー・ジェイ; ラタン・エルバート・エル |
| (57)【要約】 VTOL/STOL自在翼航空機（100）は、隣接する固定翼の胴体中心よりに各々に接続される胴体（102）、または胴体（102）に固定的に取りつけられる中心基部（117）の両側に翼を有する自在翼（110）を備え、翼幅軸（112）を中心にして旋回自在としている。 水平および垂直尾翼面（138，140）は、胴体（102）に回動可能に接続される支材装置（120）の後端に位置する。 パイロットまたは遠隔制御オペレータにより制御されるギア（150）またはねじ軸（160）機構は、尾翼支材装置（120）に対して選択的相対的に胴体（102）を旋回させて、VTOL/STOL飛行を可能にするよう胴体が傾いている状態または鼻先があがっている状態としている。 | ||||||
| 5 | Hand launchable unmanned aerial vehicle | US13790655 | 2013-03-08 | US08669504B2 | 2014-03-11 | Gerald Miller; James Stewart |
| An unmanned aerial vehicle including a controller operating in a search mode of operation where a receiver of an acquisition sensor searches for a target and causes flight control surfaces to guide the vehicle in a downward spiral path, a terminal mode of operation where the acquisition sensor detects a target and causes flight control surfaces to direct the vehicle toward the target, and an activation mode of operation where a trigger sensor detects a target within a predetermined distance to the vehicle and the controller activates a responder. | ||||||
| 6 | HAND LAUNCHABLE UNMANNED AERIAL VEHICLE | US12640585 | 2009-12-17 | US20110147515A1 | 2011-06-23 | Gerald Miller; James Stewart |
| An unmanned aerial vehicle including a controller operating in a search mode of operation where a receiver of an acquisition sensor searches for a target and causes flight control surfaces to guide the vehicle in a downward spiral path, a terminal mode of operation where the acquisition sensor detects a target and causes flight control surfaces to direct the vehicle toward the target, and an activation mode of operation where a trigger sensor detects a target within a predetermined distance to the vehicle and the controller activates a responder. | ||||||
| 7 | Stealthy duffel bag airplane | US10408981 | 2003-04-08 | US06892981B2 | 2005-05-17 | Jay Lipeles |
| The Duffel Bag Airplane is an inflatable flying wing unmanned airborne vehicle (UAV). The fuselage will house everything but the wings. The wing can be rolled up around the fuselage into a small package when deflated for easy transportation, such as by being carried in a duffle bag. Fabric construction, a small internal combustion engine with cooled exhaust, and wing warping controls combine to make the airplane inexpensive and extremely stealthy. All the usual signatures have been suppressed, which allow it to be used to make observations from close range under combat conditions. Control of this airplane is accomplished by warping the wings and is supplemented with stability augmentation. | ||||||
| 8 | Stealthy duffel bag airplane | US10408981 | 2003-04-08 | US20030192985A1 | 2003-10-16 | Jay Lipeles |
| The Duffel Bag Airplane is an inflatable flying wing unmanned airborne vehicle (UAV). The fuselage will house everything but the wings. The wing can be rolled up around the fuselage into a small package when deflated for easy transportation, such as by being carried in a duffle bag. Fabric construction, a small internal combustion engine with cooled exhaust, and wing warping controls combine to make the airplane inexpensive and extremely stealthy. All the usual signatures have been suppressed, which allow it to be used to make observations from close range under combat conditions. Control of this airplane is accomplished by warping the wings and is supplemented with stability augmentation. | ||||||
| 9 | Aircraft with deployable wing portions | US657601 | 1984-10-04 | US4659038A | 1987-04-21 | Hans-Jochen Hoeppner; Ulrich Kraemer; Michael Soelter |
| The deployment of folded down wings in an aircraft following, for example, rocket assisted launching from the container is carried out through gas pressure springs with strong attenuation in the final phase, the springs being releasably coupled to the wings for being jettisoned upon completion of deployment. | ||||||
| 10 | Ordnance delivery system and method including remotely piloted or programmable aircraft with yaw-to-turn guidance system | US292260 | 1981-08-12 | US4530476A | 1985-07-23 | Charles H. Thurber, Jr.; Frederick A. Behrens; John H. Hunton |
| A method and system for delivering ordnance to a target via a remotely piloted or programmable aircraft including a yaw-to-turn guidance system, a deployment and launching system and packaging for the aircraft are disclosed. | ||||||
| 11 | MOTOR VEHICLE WITH CAPTIVE AIRCRAFT | EP14854105 | 2014-10-15 | EP3057857A4 | 2017-07-26 | HYDE RODERICK A; WOOD LOWELL L JR; DUNCAN WILLIAM DAVID; KARE JORDIN T; MALASKA STEPHEN L; MYHRVOLD NATHAN P; PETROSKI ROBERT C; WEAVER THOMAS ALLAN |
| A motor vehicle system includes a motor vehicle including an aircraft landing portion, and an actively propelled unmanned aircraft configured to be supported on the aircraft landing portion. The vehicle and aircraft are configured such that the vehicle can provide at least one of fuel and electrical energy to the aircraft while the aircraft is supported on the aircraft landing portion. | ||||||
| 12 | MOTOR VEHICLE WITH CAPTIVE AIRCRAFT | EP14854105.5 | 2014-10-15 | EP3057857A1 | 2016-08-24 | HYDE, Roderick A.; WOOD, Lowell L., Jr.; DUNCAN, William David; KARE, Jordin T.; MALASKA, Stephen L.; MYHRVOLD, Nathan P.; PETROSKI, Robert C.; WEAVER, Thomas Allan |
| A motor vehicle system includes a motor vehicle including an aircraft landing portion, and an actively propelled unmanned aircraft configured to be supported on the aircraft landing portion. The vehicle and aircraft are configured such that the vehicle can provide at least one of fuel and electrical energy to the aircraft while the aircraft is supported on the aircraft landing portion. | ||||||
| 13 | STOL/VTOL FREE WING AIRCRAFT WITH ARTICULATED TAIL BOOM | EP94908602.0 | 1994-01-21 | EP0680436A1 | 1995-11-08 | RUTAN, Elbert, L.; SCHMITTLE, Hugh, J. |
| A VTOL/STOL free wing aircraft (100) includes a free wing (110) having wings on opposite sides of a fuselage (102) connected to one another respectively adjacent fixed wing inboard or center root sections (117) fixedly attached to the fuselage (102) for free rotation about a spanwise axis (112). Horizontal and vertical tail surfaces (138, 140) are located at the rear end of a boom assembly (120) rotatably connected to the fuselage (102). A gearing (150) or screw rod (160) arrangement controlled by the pilot or remote control operator selectively relatively pivots the fuselage (102) in relation to the tail boom assembly (120) to enable the fuselage to assume a tilted or nose up configuration to enable VTOL/STOL flight. | ||||||
| 14 | STOL/VTOL FREE WING AIRCRAFT WITH ARTICULATED TAIL BOOM | EP94908602.9 | 1994-01-21 | EP0680436B1 | 1998-11-18 | RUTAN, Elbert, L.; SCHMITTLE, Hugh, J. |
| A VTOL/STOL free wing aircraft (100) includes a free wing (110) having wings on opposite sides of a fuselage (102) connected to one another respectively adjacent fixed wing inboard or center root sections (117) fixedly attached to the fuselage (102) for free rotation about a spanwise axis (112). Horizontal and vertical tail surfaces (138, 140) are located at the rear end of a boom assembly (120) rotatably connected to the fuselage (102). A gearing (150) or screw rod (160) arrangement controlled by the pilot or remote control operator selectively relatively pivots the fuselage (102) in relation to the tail boom assembly (120) to enable the fuselage to assume a tilted or nose up configuration to enable VTOL/STOL flight. | ||||||
| 15 | THRUST VECTORING FREE WING AIRCRAFT | EP93907455.0 | 1993-03-12 | EP0629164A1 | 1994-12-21 | SCHMITTLE, Hugh J. |
| Un aéronef à décollage et à atterrissage verticaux (10) comprend une aile libre (16) constituée d'ailes situées sur les côtés opposés du fuselage (12) et interconnectées de manière à pouvoir tourner librement sans joints, dont le pas différentiel peut être ajusté par le pilote, par un ordinateur ou par télécommande. Pendant le lancement vertical, les gouvernes de profondeur (26) et de direction (24), ainsi que le réglage du pas différentiel des ailes commandent la profondeur, le lacet et le roulis, respectivement. Pendant le lancement, la gouverne de profondeur (26) incline le nez du fuselage (12) vers le bas afin de modifier le vecteur de poussée et accélérer horizontalement l'aéronef, alors que l'aile libre (16) tourne par rapport au fuselage (12) jusqu'à une position généralement horizontale afin de porter l'aéronef pendant le vol horizontal. La transition du vol horizontal au vol vertical est obtenue par le procédé inverse et l'aéronef peut être doucement récupéré dans ou sur une surface élastique telle qu'un filet (66). | ||||||
| 16 | Unbemannter Flugkörper | EP85111501.4 | 1985-09-11 | EP0185852A1 | 1986-07-02 | Dellinger, Jürgen; Höppner, Heinzjochen; Krämer, Ulrich |
Ein unbemannter Flugkörper (1) ist mit einem heckseitig angeordneten Propellerantrieb für den Marschflug sowie mit einem Raketenantriebwerk (13) für die Startphase ausgestattet, das lösbar hinter der Luftschraube (3) des Propellerantriebs gehaltert ist. Der Schub des Raketentriebwerks (13) wird Ober Schubstangen (6, 7, 26. 27) zentral auf den Flugkörperrumpf (1) übertragen, die zwischen einem das Raketentriebwerk tragenden Raketengestell und den Hinterkanten des Leitwerks sowie der Tragflächen angeordnet sind. Wenigstens zwei Schubstangen sind dabei schwenkbar am Raketengestell angelenkt und liegen mit ihren Stirnflächen formschlüssig an entsprechenden Auflagepunkten an den Tragflächen an. |
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| 17 | Aircraft with folding and/or pivoting wings | EP84103991 | 1984-04-10 | EP0141895A3 | 1986-03-05 | Höppner, Hans-Jochen; Krämer, Ulrich; Sölter, Michael |
| 18 | Luftfahrzeug mit durch Verschwenken faltbaren Tragflügeln | EP84103991.0 | 1984-04-10 | EP0141895A2 | 1985-05-22 | Höppner, Hans-Jochen; Krämer, Ulrich; Sölter, Michael |
Die Erfindung bezieht sich auf ein Luftfahrzeug mit faltbaren und/oder schwenkbaren Tragflügeln. Eine zwischen den Flügelteilen und/oder dem Rumpf angreifende Gasdruckfeder mit starker Enddämpfung sorgt für eine schnelle und automatische Entfaltung bzw. Schwenkung der Tragflügel. |
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| 19 | HILFSTRAGFLÜGELEINRICHTUNG | EP16197923.2 | 2016-11-09 | EP3168150A1 | 2017-05-17 | Maier, Franz |
Eine Hilfstragflügeleinrichtung zur Verwendung mit einem unbemannten Flugkörper (1), der einen Rumpf (10) mit einem Feststoffantrieb (11) sowie am Rumpf (10) angeordnete Flügel (12, 13, 14, 15) und Steuerflächen (16, 17, 18, 19) aufweist, zeichnet sich dadurch aus, dass die Hilfstragflügeleinrichtung (2; 102) zumindest eine aerodynamischen Auftrieb erzeugende Tragfläche (23, 24; 121, 122, 123, 124) aufweist und dass die Hilfstragflügeleinrichtung (2) einen Rumpfadapter (20; 120) aufweist, der zur Aufnahme zumindest eines Abschnitts des Rumpfs (10) des unbemannten Flugkörpers (1) oder eines Abschnitts eines den Flugkörper (1) aufnehmenden Startrohrs (100) für den Flugkörper (1) ausgebildet ist.
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| 20 | CIRCULAR VERTICAL TAKE-OFF AND LANDING AIRCRAFT | EP02703709.2 | 2002-02-26 | EP1370460A1 | 2003-12-17 | Walmsley, Eric Ronald |
| A circular VTOL aircraft with a central vertically mounted turboprop engine (14), driving contra-rotating co-axial propellers (24), above a central jet engine, or engines (12), horizontally mounted on a turntable (11) and steerable through 360 degrees. The turboprop provides vertical thrust from propellers compressing air from an upper circular intake (5) downward through a circular funnel-shaped rotor-chamber (6), to a circular vent (10) at the base of the aircraft. The resulting column of compressed air gives lift for VTOL operations and a cushion of air in flight. The horizontally mounted turbine provides acceleration, retro-thrust and directional control for horizontal flight and vectored thrust for VTOL. An alternative engine configuration (Figure 9), replaces the turboprop and propellers with a vertical turbojet or rocket-engine system providing direct vertical thrust via four control vents (12/14), with an optional horizontal vectored thrust vent (15/37). he aircraft. Fuel-tanks are installed around the central engines. The flight-deck is at the top-centre of the craft above the engines, which are detachable for maintenance. | ||||||
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